System for reducing combustion dynamics

ABSTRACT

A system and method for reducing combustion dynamics includes first and second combustors arranged about an axis, and each combustor includes a plurality of tubes that extend axially through at least a portion of the combustor and a combustion chamber downstream from the plurality of tubes. A fuel injector extends through each tube to provide fluid communication into each tube at a fourth axial distance from the combustion chamber. The fourth axial distance in the first combustor is different than the fourth axial distance in the second combustor.

FIELD OF THE INVENTION

The present invention generally involves a system and method forreducing combustion dynamics. In particular embodiments, the inventionmay be incorporated into a gas turbine or other turbo-machine.

BACKGROUND OF THE INVENTION

Combustors are commonly used in industrial and commercial operations toignite fuel to produce combustion gases having a high temperature andpressure. For example, gas turbines and other turbo-machines typicallyinclude one or more combustors to generate power or thrust. A typicalgas turbine used to generate electrical power includes an axialcompressor at the front, multiple combustors around the middle, and aturbine at the rear. Ambient air enters the compressor as a workingfluid, and the compressor progressively imparts kinetic energy to theworking fluid to produce a compressed working fluid at a highlyenergized state. The compressed working fluid exits the compressor andflows through one or more fuel nozzles and/or tubes in the combustorswhere the compressed working fluid mixes with fuel before igniting togenerate combustion gases having a high temperature and pressure. Thecombustion gases flow to the turbine where they expand to produce work.For example, expansion of the combustion gases in the turbine may rotatea shaft connected to a generator to produce electricity.

Various factors influence the design and operation of the combustors.For example, higher combustion gas temperatures generally improve thethermodynamic efficiency of the combustors. However, higher combustiongas temperatures also promote flame holding conditions in which thecombustion flame migrates toward the fuel being supplied by the fuelnozzles, possibly causing accelerated wear to the fuel nozzles in arelatively short amount of time. In addition, higher combustion gastemperatures generally increase the disassociation rate of diatomicnitrogen, increasing the production of nitrogen oxides (NO_(X)).Conversely, a lower combustion gas temperature associated with reducedfuel flow and/or part load operation (turndown) generally reduces thechemical reaction rates of the combustion gases, increasing theproduction of carbon monoxide and unburned hydrocarbons.

Although effective at enabling higher operating temperatures whileprotecting against flame holding and controlling undesirable emissions,at particular operating conditions, some combustors may producecombustion instabilities that result from an interaction or coupling ofthe combustion process or flame dynamics with one or more acousticresonant frequencies of the combustor. For example, one mechanism ofcombustion instabilities may occur when the acoustic pressure pulsationscause a mass flow fluctuation at a fuel port which then results in afuel-air ratio fluctuation in the flame zone. When the resultingfuel/air ratio fluctuation and the acoustic pressure pulsations have acertain phase behavior (e.g., approximately in-phase), a self-excitedfeedback loop results. This mechanism, and the resulting magnitude ofthe combustion dynamics, depends on the delay time between the injectionof the fuel and the time when it reaches the flame zone, known in theart as convective time (Tau). As the convective time increases, thefrequency of the combustion instabilities decreases, and when theconvective time decreases, the frequency of the combustion instabilitiesincreases. The result is combustion dynamics that may reduce the usefullife of one or more combustor and/or downstream components. For example,the combustion dynamics may produce pressure pulses inside the fuelnozzles and/or combustion chambers that may adversely affect the highcycle fatigue life of these components, the stability of the combustionflame, the design margins for flame holding, and/or undesirableemissions. Alternately, or in addition, combustion dynamics at specificfrequencies and with sufficient amplitudes, that are in-phase andcoherent, may produce undesirable sympathetic vibrations in the turbineand/or other downstream components. By shifting the frequency of thecombustion instability in one or more combustors away from the others,the coherence of the combustion system as a whole will be reduced, andthe combustor-to-combustor coupling will be diminished. This reduces theability of the combustor tone to cause a vibratory response indownstream components and also encourages destructive interference fromcombustor-to-combustor, reducing combustion dynamics amplitudes.Therefore, a system and method that adjusts the phase and/or coherenceof the combustion dynamics produced by each combustor would be useful toenhancing the thermodynamic efficiency of the combustors, protectingagainst accelerated wear, promoting flame stability, and/or reducingundesirable emissions over a wide range of operating levels.

BRIEF DESCRIPTION OF THE INVENTION

Aspects and advantages of the invention are set forth below in thefollowing description, or may be obvious from the description, or may belearned through practice of the invention.

One embodiment of the present invention is a system for reducingcombustion dynamics that includes first and second combustors arrangedabout an axis, and each combustor includes a plurality of tubes thatextend axially through at least a portion of the combustor and acombustion chamber downstream from the plurality of tubes. A fuelinjector extends through each tube to provide fluid communication intoeach tube at a fourth axial distance from the combustion chamber. Thefourth axial distance in the first combustor is different than thefourth axial distance in the second combustor.

Another embodiment of the present invention is a system for reducingcombustion dynamics that includes first and second combustors arrangedabout an axis, and each combustor includes a cap assembly that extendsradially across at least a portion of the combustor and a combustionchamber downstream from the cap assembly. Each cap assembly includes aplurality of tubes that extend axially through the cap assembly toprovide fluid communication through the cap assembly to the combustionchamber and a fuel injector that extends through each tube to providefluid communication into each tube at a fourth axial distance from thecombustion chamber. The fourth axial distance in the first combustor isdifferent than the fourth axial distance in the second combustor.

In yet another embodiment of the present invention, a system forreducing combustion dynamics includes first and second combustorsarranged about an axis, and each combustor includes a plurality of tubesthat extend axially through at least a portion of the combustor and acombustion chamber downstream from the plurality of tubes. A fuelinjector extends through each tube to provide fluid communication intoeach tube at a fourth axial distance from the combustion chamber. Thesystem further includes structure for producing a combustion instabilityfrequency in the first combustor that is different from the combustioninstability frequency in the second combustor.

Those of ordinary skill in the art will better appreciate the featuresand aspects of such embodiments, and others, upon review of thespecification.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the present invention, including thebest mode thereof to one skilled in the art, is set forth moreparticularly in the remainder of the specification, including referenceto the accompanying figures, in which:

FIG. 1 is a simplified side cross-section view of an exemplary gasturbine according to various embodiments of the present invention;

FIG. 2 is a simplified side cross-section view of an exemplary combustoraccording to various embodiments of the present invention;

FIG. 3 is an upstream plan view of the cap assembly shown in FIG. 2according to an embodiment of the present invention;

FIG. 4 is an upstream plan view of the cap assembly shown in FIG. 2according to an alternate embodiment of the present invention;

FIG. 5 is an upstream plan view of the cap assembly shown in FIG. 2according to an alternate embodiment of the present invention;

FIG. 6 is a side cross-section view of the head end of the combustorshown in FIG. 3 taken along line A-A according to an embodiment of thepresent invention;

FIG. 7 is a system for reducing combustion dynamics according to a firstembodiment of the present invention;

FIG. 8 is a system for reducing combustion dynamics according to asecond embodiment of the present invention;

FIG. 9 is a side cross-section view of the head end of the combustorshown in FIG. 5 taken along line B-B according to an embodiment of thepresent invention;

FIG. 10 is a system for reducing combustion dynamics according to athird embodiment of the present invention;

FIG. 11 is a system for reducing combustion dynamics according to afourth embodiment of the present invention; and

FIG. 12 is an exemplary graph of combustor dynamics according to variousembodiments of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

Reference will now be made in detail to present embodiments of theinvention, one or more examples of which are illustrated in theaccompanying drawings. The detailed description uses numerical andletter designations to refer to features in the drawings. Like orsimilar designations in the drawings and description have been used torefer to like or similar parts of the invention. As used herein, theterms “first”, “second”, and “third” may be used interchangeably todistinguish one component from another and are not intended to signifylocation or importance of the individual components. In addition, theterms “upstream” and “downstream” refer to the relative location ofcomponents in a fluid pathway. For example, component A is upstream fromcomponent B if a fluid flows from component A to component B.Conversely, component B is downstream from component A if component Breceives a fluid flow from component A.

Each example is provided by way of explanation of the invention, notlimitation of the invention. In fact, it will be apparent to thoseskilled in the art that modifications and variations can be made in thepresent invention without departing from the scope or spirit thereof.For instance, features illustrated or described as part of oneembodiment may be used on another embodiment to yield a still furtherembodiment. Thus, it is intended that the present invention covers suchmodifications and variations as come within the scope of the appendedclaims and their equivalents.

Various embodiments of the present invention include a system and methodfor reducing combustion dynamics to enhance thermodynamic efficiency,promote flame stability, and/or reduce undesirable emissions over a widerange of operating levels. The system and method generally includemultiple combustors, and each combustor includes one or more fuelnozzles and/or tubes and a combustion chamber downstream from the fuelnozzle(s) and/or tubes. Each fuel nozzle includes one or more fuel portsand/or radially extending vanes, and each tube includes one or more fuelinjectors. The system and method include various means for producing acombustion instability frequency in the first combustor that isdifferent from the combustion instability frequency in the secondcombustor. As a result, various embodiments of the present invention mayresult in extended operating conditions, extended life and/ormaintenance intervals, improved design margins of flame holding, and/orreduced undesirable emissions. Although exemplary embodiments of thepresent invention will be described generally in the context ofcombustion dynamics in a gas turbine for purposes of illustration, oneof ordinary skill in the art will readily appreciate that embodiments ofthe present invention may be applied to any combustion dynamics and arenot limited to a gas turbine unless specifically recited in the claims.

FIG. 1 provides a simplified cross-section view of an exemplary gasturbine 10 that may incorporate various embodiments of the presentinvention. As shown, the gas turbine 10 may generally include acompressor section 12 at the front, multiple combustors 14 radiallydisposed in a combustion section around the middle, and a turbinesection 16 at the rear. The compressor section 12 and the turbinesection 16 may share a common rotor 18 connected to a generator 20 toproduce electricity. A working fluid 22, such as ambient air, may enterthe compressor section 12 and pass through alternating stages ofstationary vanes 24 and rotating blades 26. A compressor casing 28contains the working fluid 22 as the stationary vanes 24 and rotatingblades 26 accelerate and redirect the working fluid 22 to produce acontinuous flow of compressed working fluid 22. The majority of thecompressed working fluid 22 flows through a compressor discharge plenum30 to the combustors 14. A combustor casing 32 may circumferentiallysurround some or all of each combustor 14 to contain the compressedworking fluid 22 flowing from the compressor section 12. Fuel may bemixed with the compressed working fluid 22 in one or more fuel nozzles34 and/or tubes 36. Possible fuels include, for example, one or more ofblast furnace gas, coke oven gas, natural gas, vaporized liquefiednatural gas (LNG), hydrogen, and propane. The mixture of fuel andcompressed working fluid 22 may then flow into a combustion chamber 38where it ignites to generate combustion gases having a high temperatureand pressure. A transition duct 40 circumferentially surrounds at leasta portion of the combustion chamber 38, and the combustion gases flowthrough the transition duct 40 to the turbine section 16.

The turbine section 16 may include alternating stages of stationarynozzles 42 and rotating buckets 44. The stationary nozzles 42 redirectthe combustion gases onto the next stage of rotating buckets 44, and thecombustion gases expand as they pass over the rotating buckets 44,causing the rotating buckets 44 and rotor 18 to rotate. The combustiongases then flow to the next stage of stationary nozzles 42 whichredirect the combustion gases to the next stage of rotating buckets 44,and the process repeats for the following stages.

The combustors 14 may be any type of combustor known in the art, and thepresent invention is not limited to any particular combustor designunless specifically recited in the claims. FIG. 2 provides a simplifiedside cross-section view of an exemplary combustor 14 according tovarious embodiments of the present invention. The combustor casing 32circumferentially surrounds at least a portion of the combustor 14 tocontain the compressed working fluid 22 flowing from the compressor 12.As shown in FIG. 2, the combustor casing 32 may be connected to orinclude an end cover 46 that extends radially across at least a portionof each combustor 14 to provide an interface for supplying fuel,diluent, and/or other additives to each combustor 14. In addition, thecombustor casing 32 and end cover 46 may combine to at least partiallydefine a head end 48 inside each combustor 14. The fuel nozzles 34and/or tubes 36 may be radially arranged in a cap assembly 50 thatextends radially across at least a portion of each combustor 14downstream from the head end 48. A liner 52 may be connected to the capassembly 50 to at least partially define the combustion chamber 38downstream from the cap assembly 50. In this manner, the working fluid22 may flow, for example, through flow holes 54 in an impingement sleeve56 and along the outside of the transition duct 40 and liner 52 toprovide convective cooling to the transition duct 40 and liner 52. Whenthe working fluid 22 reaches the head end 48, the working fluid 22reverses direction, and the fuel nozzles 34 and/or tubes 36 providefluid communication for the working fluid 22 to flow through the capassembly 50 and into the combustion chamber 38.

Although generally shown as cylindrical, the radial cross-section of thefuel nozzles 34 and/or tubes 36 may be any geometric shape, and thepresent invention is not limited to any particular radial cross-sectionunless specifically recited in the claims. In addition, variousembodiments of the combustor 14 may include different numbers andarrangements of fuel nozzles 34 and/or tubes 36 in the cap assembly 50,and FIGS. 3-5 provide upstream plan views of exemplary arrangements ofthe fuel nozzles 34 and/or tubes 36 in the cap assembly 50 within thescope of the present invention. As shown in FIG. 3, for example,multiple fuel nozzles 34 may be radially arranged around a single fuelnozzle 34. Alternately, as shown in FIG. 4, the tubes 36 may be radiallyarranged across the entire cap assembly 50, and the tubes 36 may bedivided into various groups to facilitate multiple fueling regimes overthe combustor's 14 range of operations. For example, the tubes 36 may begrouped in a plurality of circular tube bundles 58 thatcircumferentially surround a center tube bundle 60, as shown in FIG. 4.Alternately, as shown in FIG. 5, a plurality of pie-shaped tube bundles62 may circumferentially surround a single fuel nozzle 34. During baseload operations, fuel may be supplied to each fuel nozzle 34 and tubebundle 58, 60, 62 shown in FIGS. 3-5, while fuel flow may be reduced orcompletely eliminated from the center fuel nozzle 34 or center tubebundle 60 and/or one or more circumferentially arranged fuel nozzles 34or circular or pie-shaped tube bundles 58, 62 during reduced or turndownoperations. One of ordinary skill in the art will readily appreciatemultiple other shapes and arrangements for the fuel nozzles 34, tubes36, and tube bundles 58, 60, 62 from the teachings herein, and theparticular shape and arrangement of the fuel nozzles 34, tubes 36, andtube bundles 58, 60, 62 are not limitations of the present inventionunless specifically recited in the claims.

FIG. 6 provides a side cross-section view of the head end 48 of thecombustor 14 shown in FIG. 3 taken along line A-A according to anembodiment of the present invention. As shown in FIGS. 3 and 6, thecombustor 14 may include a plurality of fuel nozzles 34 radiallyarranged around a center fuel nozzle 34 that is substantially alignedwith an axial centerline 64 of the combustor 14. Each fuel nozzle 34 mayinclude a center body 66 that extends axially downstream from the endcover 46 and a shroud 68 that circumferentially surrounds at least aportion of the center body 66 to define an annular passage 70 betweenthe center body 66 and the shroud 68. One or more vanes 72 may extendradially between the center body 66 and the shroud 68, and the vanes 72may be angled or curved to impart swirl to the working fluid 22 flowingthrough the annular passage 70 between the center body 66 and the shroud68. The vanes 72 and/or the center body 66 may include one or more fuelports 74. In this manner, fuel may be supplied through the center body66 and/or vanes 72, and the fuel ports 74 provide fluid communicationfor the fuel to flow into the annular passage 70 and mix with theworking fluid 22 before the mixture reaches the combustion chamber 38.

When the fuel nozzles 34 are incorporated into the combustor 14, such asthe exemplary combustor 14 shown in FIG. 2, the resulting combustionprocess in the combustion chamber 38 may produce heat releasefluctuations that may in turn couple with one or more acoustic modes ofthe combustor 14, generating combustion instabilities. One specificmechanism that may produce combustion instabilities occurs when theacoustic pulsations driven by the heat release fluctuations cause massflow fluctuations through the fuel ports 74. For example, the pressurepulses associated with the combustion flames may propagate upstream fromthe combustion chamber 38 into each annular passage 70. Once thepressure pulses reach the fuel ports 74 and/or vanes 72, the pressurepulses may interfere with the fuel flow through the fuel ports 74 and/orover the vanes 72, creating fluctuations in the fuel-air mixtureconcentration flowing downstream toward the combustion flame. Thisfuel/air ratio fluctuation then travels downstream to the flame regionwhere it causes a heat release fluctuation. Provided the resulting heatrelease fluctuation is approximately in phase with the pressurefluctuations, it will further encourage heat release fluctuations,creating a continuous feedback loop. Conversely, if the resulting heatrelease fluctuation and the pressure fluctuations are out of phase,destructive interfere will decrease the magnitude of the combustioninstability frequency associated with the particular fuel nozzle 34. Thecombustion instability frequencies associated with the fuel nozzles 34may in turn either constructively or destructively interfere with oneanother to increase or decrease the amplitude of the combustion dynamicsassociated with the particular combustor 14.

The resulting combustion instability frequencies will be a function ofthe time it takes for the acoustic pressure pulse to reach the fuel portand then the resulting fuel/air ratio disturbance to reach the flamezone. This time is known in the art as convective time, or Tau. Thecombustion instability frequencies generated by the interaction of thefuel/air ratio fluctuations and the acoustic pressure fluctuation aretherefore inversely proportional to the axial distance between the fuelports 74 and/or the vanes 72 and the combustion chamber 38 (i.e., theend of the fuel nozzles 34 or the end of the shrouds 68). In particularembodiments, these combustion instability frequencies may be adjustedand/or tuned in one or more fuel nozzles 34 to affect the combustiondynamics associated with the individual combustor 14. In the particularembodiment shown in FIGS. 3 and 6, for example, the combustor 14 mayinclude multiple fuel nozzles 34, with a different axial distance 76between the fuel ports 74 and/or the vanes 72 and the combustion chamber38 for each fuel nozzle 34. As a result, the combustion instabilityfrequency generated for each fuel nozzle 34 will be slightly different,reducing or precluding constructive interference between the fuelnozzles 34 from increasing the amplitude of the combustion dynamicsassociated with the particular combustor 14. One of ordinary skill inthe art will readily appreciate from the teachings herein that multiplecombinations of variations in the axial distances 76 between the fuelports 74 and/or the vanes 72 and the combustion chamber 38 are possibleto achieve a desired combustion instability frequency for each fuelnozzle 34 and/or desired combustion dynamics for the particularcombustor 14. For example, in particular embodiments, the axialdistances 76 between the fuel ports 74 and/or the vanes 72 and thecombustion chamber 38 may be the same or different for some or all ofthe fuel nozzles 34 in a particular combustor 14, and the presentinvention is not limited to any particular combination of axialdistances 76 unless specifically recited in the claims.

The combustion dynamics associated with multiple combustors 14incorporated into the gas turbine 10 may in turn either constructivelyor destructively interfere with one another to increase or decrease theamplitude and/or coherence of the combustion dynamics associated withthe gas turbine 10. In particular embodiments, the combustioninstability frequencies and/or combustion dynamics associated with oneor more combustors 14 may be adjusted and/or tuned to affect theinteraction with the combustion dynamics of another combustor 14 andthus the combustion dynamics associated with the gas turbine 10. Forexample, FIG. 7 provides a system for reducing combustion dynamicsand/or coherence of the combustion dynamics according to a firstembodiment of the present invention. In the particular embodiment shownin FIG. 7, multiple combustors 14 as shown in FIGS. 3 and 6 have beenarranged about an axis 78. The axis 78 may coincide, for example, withthe rotor 18 in the gas turbine 10 that connects the compressor section12 to the turbine section 16, although the present invention is notlimited to the particular orientation of the axis 78 or the particulararrangement of the combustors 14 about the axis 78.

As shown in FIG. 7, each combustor 14 includes multiple fuel nozzles 34with the combustion chamber 38 downstream from the fuel nozzles 34 aspreviously described with respect to FIGS. 2, 3, and 6. In addition, thesystem further includes means for producing a combustion instabilityfrequency in one combustor 14 that is different from the combustioninstability frequency in the other combustor 14. The function ofproducing a combustion instability frequency in one combustor 14 that isdifferent from the combustion instability frequency in the othercombustor 14 reduces or prevents coherent or constructive interferencebetween the combustion instability frequencies that might increase theamplitude of the combustion dynamics or increase the coherence of thecombustion dynamics of two or more combustors 14. The structure for themeans may include a difference in one or more of the axial distances 76between the fuel ports 74 and the combustion chamber 38 and/or the vanes72 and the combustion chamber 38 between the two combustors 14. In theparticular embodiment shown in FIG. 7, for example, each axial distance76 between the fuel ports 74 and the combustion chamber 38 and betweenthe vanes 72 and the combustion chamber 38 is different between the twocombustors 14. As a result, the means produces different combustioninstability frequencies in the two combustors 14. One of ordinary skillin the art will readily appreciate from the teachings herein thatmultiple combinations of variations in the axial distances 76 betweenthe fuel ports 74 and the combustion chamber 38 and/or the vanes 72 andthe combustion chamber 38 are possible to produce a combustioninstability frequency in one combustor 14 that is different from thecombustion instability frequency in the other combustor 14. For example,in particular embodiments, one or more axial distances 76 between thefuel ports 74 and the combustion chamber 38 and/or the vanes 72 and thecombustion chamber 38 may be the same or different for one or more ofthe fuel nozzles 34 in a particular combustor 14 compared to the othercombustor 14, as long as the axial distances 76 are not all the samebetween both combustors 14, and the present invention is not limited toany particular combination of axial distances 76 unless specificallyrecited in the claims.

FIG. 8 provides a system for reducing combustion dynamics according to asecond embodiment of the present invention. As shown in FIG. 8, eachcombustor 14 again includes multiple fuel nozzles 34 with the combustionchamber 38 downstream from the fuel nozzles 34 as previously describedwith respect to FIGS. 2, 3, 6 and 7. In addition, the axial positions ofthe fuel ports 74 and/or the vanes 72 may be the same or different ineach combustor 14. In the specific embodiment shown in FIG. 8, forexample, the axial positions of the fuel ports 74 and the vanes 72 aredifferent within the same combustor 14, but the axial positions of thefuel ports 74 and the vanes 72 are repeated in both of the combustors14.

The embodiment shown in FIG. 8 again includes means for producing acombustion instability frequency or resonant frequency in one combustor14 that is different from the combustion instability frequency orresonant frequency in the other combustor 14. In this particularembodiment, the structure for the means may include a difference in anaxial length 80 of the cap assembly 50 in one combustor 14 compared tothe axial length 80 of the cap assembly in the other combustor 14. Withthe axial positions of the fuel ports 74 and the vanes 72 repeated inboth of the combustors 14, the difference in the axial lengths 80between the two combustors 14 produces a corresponding difference in theaxial distances 76 between the fuel ports 74 and the combustion chamber38 and the vanes 72 and the combustion chamber 38 between the twocombustors 14. The difference in axial distances 76 between the twocombustors 14 produces a corresponding difference in the combustioninstability or resonant frequencies between the two combustors 14. Oneof ordinary skill in the art will readily appreciate from the teachingsherein that multiple combinations of variations in the axial distances76 between the fuel ports 74 and the combustion chamber 38 and/or thevanes 72 and the combustion chamber 38 are possible to produce acombustion instability or resonant frequency in one combustor 14 that isdifferent from the combustion instability or resonant frequency in theother combustor 14. For example, in particular embodiments, one or moreaxial distances 76 between the fuel ports 74 and the combustion chamber38 and/or the vanes 72 and the combustion chamber 38 may be the same ordifferent for one or more of the fuel nozzles 34 in a particularcombustor 14 compared to the other combustor 14, and the presentinvention is not limited to any particular combination of axialdistances 76 unless specifically recited in the claims.

FIG. 9 provides a side cross-section view of the head end 48 of thecombustor 14 shown in FIG. 5 taken along line B-B according to anembodiment of the present invention. As shown, the cap assembly 50extends radially across at least a portion of the combustor 14 andincludes an upstream surface 82 axially separated from a downstreamsurface 84. The upstream and downstream surfaces 82, 84 may be generallyflat or straight and oriented perpendicular to the general flow of theworking fluid 22 through the cap assembly 50. In the particularembodiment shown in FIG. 9, the fuel nozzle 34 is again substantiallyaligned with the axial centerline 64 of the cap assembly 50 and extendsthrough the cap assembly 50 to provide fluid communication through thecap assembly 50 to the combustion chamber 38. The fuel nozzle 34 mayinclude any suitable structure known to one of ordinary skill in the artfor mixing fuel with the working fluid 22 prior to entry into thecombustion chamber 38, and the present invention is not limited to anyparticular structure or design unless specifically recited in theclaims. For example, as shown in FIG. 9, the fuel nozzle 34 may includethe center body 66, shroud 68, annular passage 70, vanes 72, and fuelports 74 as previously described with respect to the embodiment shown inFIG. 6.

As shown in FIGS. 5 and 9, the tubes 36 may be circumferentiallyarranged around the fuel nozzle 34 in pie-shaped tube bundles 62 and mayextend from the upstream surface 82 through the downstream surface 84 ofthe cap assembly 50. Each tube 36 generally includes an inlet 86proximate to the upstream surface 82 and an outlet 88 proximate to thedownstream surface 84 to provide fluid communication through the capassembly 50 and into the combustion chamber 38 downstream from the tubes36.

As shown in FIG. 9, the upstream and downstream surfaces 82, 84 may atleast partially define a fuel plenum 90 inside the cap assembly 50. Afuel conduit 92 may extend from the casing 32 and/or the end cover 46through the upstream surface 82 to provide fluid communication for fuelto flow into the fuel plenum 90. One or more of the tubes 36 may includea fuel injector 94 that extends through the tubes 36 to provide fluidcommunication from the fuel plenum 90 into the tubes 36. The fuelinjectors 94 may be angled radially, axially, and/or azimuthally toproject and/or impart swirl to the fuel flowing through the fuelinjectors 94 and into the tubes 36. The working fluid 22 may thus flowinto the tube inlets 86, and fuel from the fuel conduit 92 may flowaround the tubes 36 in the fuel plenum 90 to provide convective coolingto the tubes 36 before flowing through the fuel injectors 94 and intothe tubes 36 to mix with the working fluid 22. The fuel-working fluidmixture may then flow through the tubes 36 and into the combustionchamber 38.

As previously described with respect to the embodiment shown in FIG. 6,when the tubes 36 are incorporated into the combustor 14, such as theexemplary combustor 14 shown in FIG. 2, the resulting combustion processin the combustion chamber 38 may produce heat release fluctuations thatmay in turn couple with one or more acoustic modes of the combustor 14,generating combustion instabilities. One specific mechanism by whichcombustion instabilities may be produced occur when the acousticpulsations driven by the heat release fluctuations travel upstream tothe fuel injectors 94 where they may interfere with the fuel flowthrough the fuel injectors 94 and create fluctuations in the fuel-airmixture concentration flowing downstream toward the combustion flame.This fuel/air ratio fluctuation then travels downstream to the flameregion where it can cause a heat release fluctuation. Provided theresulting heat release fluctuation is approximately in-phase with thepressure fluctuations, it will further encourage heat releasefluctuations, completing a continuous feedback loop. Conversely, if theresulting heat release fluctuation and the pressure fluctuations are outof phase, destructive interfere will decrease the magnitude of thecombustion instability frequency associated with the tubes 36, tubebundles 62, and/or cap assembly 50. The combustion instabilityfrequencies associated with the tubes 36 and/or tube bundles 62 may inturn either constructively or destructively interfere with one anotherto increase or decrease the amplitude of the combustion dynamicsassociated with the particular combustor 14.

The resulting combustion instability frequencies will be a function ofthe time it takes for the acoustic pressure pulse to reach the fuelinjector 94 and then the resulting fuel/air ratio disturbance to reachthe flame zone. This time is known in the art as convective time, orTau. The combustion instability frequencies generated by the interactionof the fuel/air ratio fluctuations and the acoustic pressure fluctuationare therefore inversely proportional to the axial distance between thefuel injectors 94 and the combustion chamber 38 (i.e., the tube outlets88). In particular embodiments, these combustion instability frequenciesmay be adjusted and/or tuned in one or more tubes 36 and/or tube bundles62 to affect the combustion dynamics associated with the individualcombustor 14. In the particular embodiment shown in FIGS. 5 and 9, forexample, the tubes 36 may have a different axial distance 96 between thefuel injectors 94 and the combustion chamber 38 for each tube bundle 62.As a result, the combustion instability frequency for each tube 62 willbe slightly different, reducing or precluding constructive interferencebetween the tube bundles 62 from increasing the amplitude of thecombustion dynamics associated with the particular combustor 14. One ofordinary skill in the art will readily appreciate from the teachingsherein that multiple combinations of variations in the axial distances96 between the fuel injectors 94 and the combustion chamber 38 arepossible to achieve a desired combustion instability frequency for eachtube 36 and/or tube bundle 62 and/or desired combustion dynamics for theparticular combustor 14. For example, in particular embodiments, theaxial distances 96 between the fuel injectors 94 and the combustionchamber 38 may be the same or different for some or all of the tubes 36and/or tube bundles 62 in a particular combustor 14, and the presentinvention is not limited to any particular combination of axialdistances 96 unless specifically recited in the claims.

The combustion dynamics associated with multiple combustors 14incorporated into the gas turbine 10 may in turn either constructivelyor destructively interfere with one another to increase or decrease theamplitude and/or coherence of the combustion dynamics associated withthe gas turbine 10. In particular embodiments, the combustioninstability frequencies and/or combustion dynamics associated with oneor more combustors 14 may be adjusted and/or tuned to affect theinteraction with the combustion dynamics of another combustor 14 andthus the combustion dynamics associated with the gas turbine 10. Forexample, FIG. 10 provides a system for reducing combustion dynamicsaccording to a third embodiment of the present invention. In theparticular embodiment shown in FIG. 10, multiple combustors 14 as shownin FIGS. 5 and 9 have been arranged about an axis 100. The axis 100 maycoincide, for example, with the rotor 18 in the gas turbine 10 thatconnects the compressor section 12 to the turbine section 16, althoughthe present invention is not limited to the particular orientation ofthe axis 100 or the particular arrangement of the combustors 14 aboutthe axis 100.

As shown in FIG. 10, each combustor 14 includes multiple tubes 36arranged in pie-shaped tube bundles 62 that circumferentially surroundthe fuel nozzle 34, and the combustion chamber 38 is downstream from thetubes 36, tube bundles 62, and fuel nozzle 34 as previously describedwith respect to FIGS. 2, 5, and 9. In addition, the system furtherincludes means for producing a combustion instability frequency in onecombustor 14 that is different from the combustion instability frequencyin the other combustor 14. The structure for the means may include adifference in one or more of the axial distances 96 between the fuelinjectors 94 and the combustion chamber 38 between the two combustors14. In the particular embodiment shown in FIG. 10, for example, theaxial distance 96 between the fuel injectors 94 and the combustionchamber 38 for each tube bundle 62 is different between the twocombustors 14. As a result, the means produces different combustioninstability frequencies in the two combustors 14. One of ordinary skillin the art will readily appreciate from the teachings herein thatmultiple combinations of variations in the axial distances 96 betweenthe fuel injectors 94 and the combustion chamber 38 are possible toproduce a combustion instability frequency in one combustor 14 that isdifferent from the combustion instability frequency in the othercombustor 14. For example, in particular embodiments, one or more axialdistances 96 between the fuel injectors 94 and the combustion chamber 38may be the same or different for one or more of the tubes 36 and/or tubebundles 62 in a particular combustor 14 compared to the other combustor14, as long as the axial distances 96 are not all the same between bothcombustors 14, and the present invention is not limited to anyparticular combination of axial distances 96 unless specifically recitedin the claims.

FIG. 11 provides a system for reducing combustion dynamics according toa fourth embodiment of the present invention. As shown in FIG. 11, eachcombustor 14 again includes multiple tubes 36 arranged in pie-shapedtube bundles 62 that circumferentially surround the fuel nozzle 34, andthe combustion chamber 38 is downstream from the tubes 36, tube bundles62, and fuel nozzle 34 as previously described with respect to FIGS. 2,5, 9, and 10. In addition, the axial positions of the fuel injectors 94may be the same or different in each combustor 14. In the specificembodiment shown in FIG. 11, for example, the axial positions of thefuel injectors 94 are different for each tube bundle 62 within the samecombustor 14, but the axial positions of the fuel injectors 94 for eachtube bundle 62 are repeated in both of the combustors 14.

The embodiment shown in FIG. 11 again includes means for producing acombustion instability or resonant frequency in one combustor 14 that isdifferent from the combustion instability or resonant frequency in theother combustor 14. As with the previous embodiment described andillustrated in FIG. 8, the structure for the means may include adifference in the axial length 80 of the cap assembly 50 in onecombustor 14 compared to the axial length 80 of the cap assembly in theother combustor 14. With the axial positions of the fuel injectors 94repeated in both of the combustors 14, the difference in the axiallengths 80 between the two combustors 14 produces a correspondingdifference in the axial distances 96 between the fuel injectors 94 andthe combustion chamber 38 between the two combustors 14. The differencein axial distances 96 between the two combustors 14 produces acorresponding difference in the combustion instability or resonantfrequencies between the two combustors 14. One of ordinary skill in theart will readily appreciate from the teachings herein that multiplecombinations of variations in the axial distances 96 between the fuelinjectors 94 and the combustion chamber 38 are possible to produce acombustion instability or resonant frequency in one combustor 14 that isdifferent from the combustion instability or resonant frequency in theother combustor 14. For example, in particular embodiments, one or moreaxial distances 96 between the fuel injectors 94 and the combustionchamber 38 may be the same or different for one or more of the tubes 36and/or tube bundles 62 in a particular combustor 14 compared to theother combustor 14, and the present invention is not limited to anyparticular combination of axial distances 96 unless specifically recitedin the claims.

FIG. 12 provides an exemplary graph of combustor dynamics according tovarious embodiments of the present invention. The horizontal axisrepresents a range of combustion instability or resonant frequencies,and the vertical axis represents a range of amplitudes. The systemdepicted in FIG. 12 may include three or more combustors 14 incorporatedinto the gas turbine 10 or other turbo-machine. Using the means forproducing a combustion instability frequency in one combustor 14 that isdifferent from the combustion instability frequency in the othercombustor 14, each combustor 14 may be adjusted or tuned to achieve adesired combustion instability frequency or combustion dynamics. Asshown in FIG. 12, for example, a first group of the combustors 14 may beadjusted and/or tuned to achieve a first combustion instabilityfrequency 102, a second group of the combustors 14 may be adjustedand/or tuned to achieve a second combustion instability frequency 104,and a third group of the combustors 14 may be adjusted and/or tuned toachieve a third combustion instability frequency 106. The first, second,and third combustion instability frequencies 102, 104, 106 are slightlydifferent from one another and therefore slightly out of phase with oneanother. As a result, the combustion instability frequencies 102, 104,106 associated with the combustors 14 cannot coherently orconstructively interfere with one another, reducing or preventing anincrease in the combustion dynamics and/or reducing the ability of thecombustion system to drive sympathetic vibrations in the downstreamturbine section 16.

One of ordinary skill in the art will readily appreciate from theteachings herein that the various structures described and illustratedwith respect to FIGS. 1-11 may provide one or more methods for reducingcombustion dynamics and/or reducing the coherence of the combustiondynamics for two or more combustors 14. The methods may include, forexample, flowing the working fluid 22 and fuel through one or more fuelnozzles 34, tubes 36, and/or tube bundles 62 into the combustionchambers 38 of multiple combustors 14. In particular embodiments, themethod may include varying one or more of the axial distances 76 betweenthe fuel ports 74 and the combustion chamber 38 and/or the vanes 72 andthe combustion chamber 38, as long as the axial distances 76 are not allthe same between all of the combustors 14, to produce a combustioninstability frequency in one combustor 14 that is different from thecombustion instability frequency in the other combustors 14. In otherparticular embodiments, the method may include varying one or more ofthe axial distances 96 between the fuel injectors 94 and the combustionchamber 38, as long as the axial distances 96 are not all the samebetween all of the combustors 14, to produce a combustion instabilityfrequency in one combustor 14 that is different from the combustioninstability frequency in the other combustor 14. In still furtherparticular embodiments, the method may include varying one or more ofthe axial lengths 80 of the cap assembly 50, as long as the axiallengths 80 are not all the same between all combustors 14, to produce acombustion instability frequency in one combustor 14 that is differentfrom the combustion instability frequency in the other combustor 14.

The various embodiments described and illustrated with respect to FIGS.1-12 may provide one or more of the following advantages over existingcombustors 14. Specifically, the different axial distances 76, 96 and/oraxial lengths 80, alone or in various combinations, may decouple thecombustion instability frequencies of the combustion dynamics. As aresult, the various embodiments described herein may enhancethermodynamic efficiency, promote flame stability, and/or reduceundesirable emissions over a wide range of operating levels.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they include structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal language of the claims.

What is claimed is:
 1. A gas turbine, comprising: a. a plurality ofcombustors annularly arranged about an axial centerline of the gasturbine, the plurality of combustors including a first combustor and asecond combustor; b. wherein the first combustor comprises a pluralityof bundled tube fuel nozzles annularly arranged about a centerline ofthe first combustor, each bundled tube fuel nozzle including a fuelplenum and a plurality of tubes which extend therethrough, each tubehaving an inlet upstream from the fuel plenum, an outlet downstream fromthe fuel plenum and a fuel injector which provides for fluidcommunication between the fuel plenum and the tube, the fuel injectorbeing disposed at a first axial distance from the tube outlet, and eachtube having the same first axial distance; c. wherein the secondcombustor comprises a plurality of bundled tube fuel nozzles annularlyarranged around a centerline of the second combustor, each bundled tubefuel nozzle including a fuel plenum and a plurality of tubes whichextend therethrough, each tube having an inlet upstream from the fuelplenum, an outlet downstream from the fuel plenum and a fuel injectorwhich provides for fluid communication between the fuel plenum and thetube, the fuel injector being disposed at a first axial distance fromthe tube outlet, and each tube having the same first axial distance; andd. wherein the first axial distance of one of the plurality of bundledtube fuel nozzles of the first combustor is different than the firstaxial distance of one of the plurality of bundled tube fuel nozzles ofthe second combustor.
 2. The gas turbine as in claim 1, wherein theplurality of bundled tube fuel nozzles of the first combustor includes afirst bundled tube fuel nozzle and a second bundled tube fuel nozzle,wherein the first axial distance of the first bundled tube fuel nozzleis different from the first axial distance of the second bundled tubefuel nozzle.
 3. The gas turbine as in claim 1, wherein the plurality ofbundled tube fuel nozzles of the second combustor includes a firstbundled tube fuel nozzle and a second bundled tube fuel nozzle, whereinthe first axial distance of the first bundled tube fuel nozzle isdifferent from the first axial distance of the second bundled tube fuelnozzle.
 4. The gas turbine as in claim 1, wherein each of the first andsecond combustors include a center fuel nozzle circumferentiallysurrounded by the corresponding plurality of bundled tube fuel nozzles.5. The gas turbine as in claim 4, wherein each center fuel nozzle is abundled tube fuel nozzle.
 6. The gas turbine as in claim 4, wherein eachcenter fuel nozzle of the first and second combustors includes a centerbody, a shroud which extends around a portion of the center body and aplurality of vanes which extend from the center body to the shroud, theshroud defining an annular passage therebetween.
 7. The gas turbine asin claim 6, wherein the center fuel nozzle of the first combustorincludes a first fuel port through at least one of the plurality ofvanes at a first axial distance from a combustion chamber defined withinthe first combustor, a second fuel port through the center bodyproximate to a tip portion of the center body at a second axial distancefrom the combustion chamber, and the plurality of vanes are at a thirdaxial distance from the combustion chamber.
 8. The gas turbine as inclaim 7, wherein the center fuel nozzle of the second combustor includesa first fuel port through at least one of the plurality of vanes at afirst axial distance from a combustion chamber defined within the secondcombustor, a second fuel port through the center body proximate to a tipportion of the center body at a second axial distance from thecombustion chamber, and the plurality of vanes are at a third axialdistance from the combustion chamber.
 9. The gas turbine as in claim 8,wherein the first axial distance of the center fuel nozzle of the firstcombustor is different from the first axial distance of the center fuelnozzle of the second combustor.
 10. The gas turbine as in claim 8,wherein the second axial distance of the center fuel nozzle of the firstcombustor is different from the second axial distance of the center fuelnozzle of the second combustor.
 11. The gas turbine as in claim 8,wherein the third axial distance of the center fuel nozzle of the firstcombustor is different from the third axial distance of the center fuelnozzle of the second combustor.
 12. The gas turbine as in claim 8,wherein the first and second combustors each include a cap assembly thatcircumferentially surrounds the plurality of bundled tube fuel nozzles,wherein each cap assembly has an axial length, wherein the axial lengthof the cap assembly in the first combustor is different than the axiallength of the cap assembly in the second combustor.
 13. A combustor,comprising: a. a first bundled tube fuel nozzle and a second bundledtube fuel nozzle arranged about a centerline of the combustor andextending axially within the combustor; b. wherein the first bundledtube fuel nozzle includes a fuel plenum and a plurality of axiallyextending tubes which extend therethrough, each tube having an inletupstream from the fuel plenum, an outlet downstream from the fuel plenumand a fuel injector which provides for fluid communication between thefuel plenum and the tube, the fuel injector being disposed at a firstaxial distance from the tube outlet, and each tube having the same firstaxial distance; c. wherein the second bundled tube fuel nozzle includesa fuel plenum and a plurality of axially extending tubes which extendtherethrough, each tube having an inlet upstream from the fuel plenum,an outlet downstream from the fuel plenum and a fuel injector whichprovides for fluid communication between the fuel plenum and the tube,the fuel injector being disposed at a first axial distance from the tubeoutlet, and each tube having the same first axial distance; d. whereinthe first axial distance of the first bundled tube fuel nozzle isdifferent from the first axial distance of the second bundled tube fuelnozzle.
 14. The combustor as in claim 13, wherein the combustor includesa center fuel nozzle circumferentially surrounded by the first andsecond bundled tube fuel nozzles.
 15. The combustor as in claim 14,wherein the center fuel nozzle is a bundled tube fuel nozzle.
 16. Thecombustor as in claim 14, wherein the center fuel nozzle includes acenter body, a shroud which extends around a portion of the center bodyand a plurality of vanes which extend from the center body to theshroud, the shroud defining an annular passage therebetween.
 17. Thecombustor as in claim 16, wherein the center fuel nozzle includes afirst fuel port through at least one of the plurality of vanes at afirst axial distance from a combustion chamber defined within the firstcombustor, a second fuel port through the center body proximate to a tipportion of the center body at a second axial distance from thecombustion chamber, and the plurality of vanes are at a third axialdistance from the combustion chamber.
 18. The combustor as in claim 17,wherein the first axial distance of the center fuel nozzle is differentfrom the first axial distance of at least one of the first bundled tubefuel nozzle and the second bundled tube fuel nozzle.
 19. The combustoras in claim 17, wherein the second axial distance of the center fuelnozzle is different from the first axial distance of at least one of thefirst bundled tube fuel nozzle and the second bundled tube fuel nozzle.20. The combustor as in claim 17, wherein the third axial distance ofthe center fuel nozzle is different from the first axial distance of atleast one of the first bundled tube fuel nozzle and the second bundledtube fuel nozzle.